Self-powered timing system for space vehicles



A. L. KORR 3,447,384

SELF'POWERED TIMING SYSTEM FOR SPACE VEHICLES June 3, 1969 Filed Sept. 25, 1967 .253. no 22815 SE8 2:;

INVENTOR. Abra/1am 1..

wodmw Korr "roman United States Patent 3,447,384 SELF-POWERED TIMING SYSTEM FOR SPACE VEHICLES Abraham L. Korr, 8712 Hickory Drive, Philadelphia, Pa. 19136 Filed Sept. 25, 1967, Ser. No. 670,479 Int. Cl. F1611 /78 US. Cl. 743.5 7 Claims ABSTRACT OF THE DISCLOSURE A piston in an air or like fluid-pressure cylinder is provided as an inertial mass which moves from a forward piston of rest in response to the setback force of launching and stores energy in a compression spring which then drives it forward. The piston is permitted to move forward at a rate dependent upon how rapidly the air or fluid pressure from the cylinder is released through an outlet conduit. The conduit is connected into a rotary timing or pallet disk having a plurality evenly-spaced radial air-jet openings or outlet ports around the periphery from which the air or fluid pressure finally escapes. The release of air or fluid pressure through the successive outlet ports and the rotation of the pallet disk is step-by-step for timing under control of an oscillatory pallet-type valve element associated therewith. The pallet disk is driven as a result of the piston movement, through a gear rack that meshes with and drives a gear train connected with a shaft on which the disk is mounted. The timing system is thus selfpowered and provides timing air or fluid pressure and mechanical drive from movement of the same inertial piston element. The return movement of the piston element at or near the position of rest serves to elfect timed operation of a switch or other function control device and thus provides a timed output from the system.

The invention described herein may be manufactured, used, and licensed by or for the Government for governmental purposes without the payment to me of any royalty thereon.

The present invention relates to timing systems of the type adapted to provide a control function or timing out put at the end of a predetermined time interval after being set into operation, and more particularly to timing systems of that type for space vehicles which follow a flight path or trajectory in motion and provide a setback force upon being launched or fired.

It is an object of the invention to provide an improved timing system of the type referred to which is self-powered in response to setback and provides a self-timing operation through the interrupted flow of compressed air or other gaseous fluid.

It is also a further object of this invention to provide a self-powered timing system for use in space vehicles, such as projectiles, which is responsive to setback force upon launching or firing to inertially effect air compression and a control movement for the release thereof in a step-by-step timing sequence.

Most timing systems utilized some means for storing potential energy which is slowly released as a driving force to a movable element forming part of the timing means. In conventional timers it is customary to store potential energy by winding a spring manually and producing rotary motion therefrom as the spring unwinds. Such motive means is not adapted for operation in a self-powered timing system.

It is therefore a further object of this invention to provide a timing system for space vehicles and the like which is inertially self-powered and responsive to air pressure and motion generated by inertial mass movement following initial setback.

Fee

In accordance with the invention, fluid pressure operated piston and cylinder means is provided to apply torque to a transmission system mechanically through a gear train. The synchronous output or driving motion of the gear train is limited by fluid pressure outlet jets in a rotary control element driven thereby and jet-operated synchronously-oscillating escapement means in conjunction therewith. This pallet-type outlet means thus operates to release fluid pressure from the cylinder in a stepby-step mode.

A relatively heavy piston element is provided as an inertial mass adapted to be axially aligned with the direction of movement or longitudinal axis of a space vehicle by which the timing system is carried, and subjected to setback force on launching or firing of the vehicle into flight to compress and store energy in spring means associated therewith. This, in turn, applies the restoring movement to the piston to provide the mechanical drive and air release. The uniform and constant frequency of oscillation of the escapement means provides the constant stepby-step time motion of the controlled element.

The invention will further be understood from the following description when considered with reference to the accompanying drawings, and its scope is pointed out in the appended claims.

In the drawings,

FIG. 1 is a schematic representation of a space vehicle fitted with a timing system utilizing an inertial mass in accordance with the invention,

FIG. 2 is a schematic mechanical representation of a complete timing system as shown in outline form in FIG. 1, illustrating a present preferred embodiment of the invention.

FIG. 3 is an end View, in elevation, of a portion of the mechanism of FIG. 2 showing further details thereof in accordance with the invention, and

FIG. 4 is an enlarged fragmentary view of a portion of the mechanism of FIG. 2. in greater detail, and showing the mode of operation thereof in accordance with the invention.

Referring to the drawings, wherein like elements through the various figures are designated by like reference numerals and characters, and referring particularly to FIG. 1, the forward end of a space vehicle is shown at 5 and represents a projectile or rocket for example, carrying an interior timing system 6 which is self-powered through gaseous fluid control under operation of an inertial mass or piston element 7. Following the setback force P, which is applied to the mass M on launching or firing of the vehicle, a timing output as indicated is produced thereby in any suitable form, such as the triggering or firing of a charge or other function in the vehicle.

Referring now to FIGS. 2 and 3 along with FIG. 1 the interior of the timing system 6 includes the piston element or inertial mass 7 which is responsive to the setback force F on launching or firing and moves rearwardly or to the right as viewed in the drawing, to store energy to com-' pressing a return or driving spring 3 against the end plate 9 of a closed cylinder 19. As the piston element 7 moves rearwardly in response to the inertial force, a springloaded valve element 11 opens to permit air or other gaseous fluid to enter the cylinder 10 through the valve opening 12. When the piston reaches the rearward limit, established by a fixed stop ring 7A, the spring 8 is fully compressed or loaded and the valve 11 closes. Breathe openings 9A are provided in the end plate to relieve the space in rear of the piston and thus to permit it to move without restraint in operation.

The piston element 7 is connected with a piston rod 15 which extends outwardly of the cylinder through a packing or bushing 16 to connect with a movable gear rack 17 which is guided to move in the direction of the arrow. The piston rod is connected directly to a block or lug 18 which provides the driving connection with the rack 17. The lug 18 is arranged to operate a suitable function control device 19 of the vehicle, such as for firing an explosive charge. In this case the device 19 is a firing switch having a depressible operating button 20 which is engaged by the lug 18 at the limit of its forward travel 18A, that is to the left in the drawing, as the piston moves. The device 19 is provided with circuit leads 21 which may be connected into any suitable circuit for controlling the firing or other function of the vehicle. In FIG. 2, the operating button is shown protected by a releasable safety block 26 which is held in place by a safety finger 22 on the lug 18 as shown at 22A. A forward driving ratchet means 27 is provided between the lug 18 and the rack 17, as shown, to permit the lug 18 to move, on launching, from the position of rest or the unarmed position at 18A, to the driving position at 18 as the piston element retracts to the right due to inertial force. The ratchet then drives to the left as the piston element and rod move forward. In the drawing this is in the direction of the arrow. The safety block 26 drops out and the switch 19 is armed and ready to operate.

The movement of the gear rack 17, for-ward in the direction of the arrow, serves to drive a gear train comprising a first gear element 23 which meshes with the gear rack 17, and an intermediate gear element '24 between the first gear element and a third gear element 25 mounted on and pinned to an output shaft 28 for the gear train.

The shaft 28 is mounted to rotate in a fixed pedestal bearing or bearing bracket 29 having a fixed supporting base plate 29A. The gear 25 is on one end of the shaft 28 while a circular rotary valve plate or disk 30 is mounted on and secured to the opposite end thereof to rotate therewith. The rotary valve plate 30 is in sliding or rotating contact with a fixed valve plate 31, of the same circular shape and also relatively thick, which is fixed in place on the base plate 29A in axial alignment with the plate 20, as indicated more clearly in FIG. 3.

The rotary valve plate or disk 30 is provided with a plurality of radial fluid or airjet outlet ports 32 uniformly, angularly spaced around the periphery thereof as indicated more clearly in FIG. 3. These outlet ports are each in communication with a corresponding inlet opening or port 34 on the inner face of the disk 30, facing the fixed disk or plate 31, as indicated in FIG. 1 and also in FIG. 4 to which attention is now directed along with the preceding figures. The inlet ports 34 are arranged in a uniform concentric ring about the axis of the shaft 28, as indicated in FIG. 1, and move with the disk 30 on the shaft 28 in a circular path which crosses over an active operating area including a fluid pressure supply chamber 33 on the contacting or inner face of the fixed valve plate 31. The fluid pressure medium used is generally a light gas or air, and in the present example may be considered to be air. The chamber 33 is in communication with the supply conduit 14 and includes two spaced radial arms 33B and 33A extending therefrom into the path of the moving inlet ports of the rotary valve plate 30 all as shown more clearly in FIG. 4.

The active operating area around the inlet chamber 33 thus includes the two spaced radially extending, arms 33A and 33B which lie directly in the path of the inlet ports 64 as the valve plate 30 rotates. The arms 33A and 33B are angularly spaced apart one half the angular distance between adjacent ports 34 as shown in FIG. 4 for example, so that while one arm 33A is in communication with a port designated as 34A for example, the arm 33B is cut off and lies midway between the port 34A and the next adjacent one, here designated as 34B in the active area of operation around the chamber 33. As the port 34A comes into registration with the chamber arm 33A the fluid pressure, that is, the air or gas is permitted to escape from the conduit 14 through the chamber 33 and out the then active outlet port here designated as 32A. The port 34A then passes out 4 of registration with the arm 33A as the port 34B comes into registration with the chamber arm 33B. The fluid pressure or air pressure then finds an outlet through the then active outlet port indicated at 32B.

The two outlet ports 32A and 32B, as above described, and the successive following ports as the disk 30 rotates, are alternately blocked or closed by a pivoted pallet element 35. This is provided with balanced pallet arms 38 and with a horizontal pivot shaft 36 closely adjacent to the peripheral face of the valve plate 30 in the area directly opposite the position of the chamber 33. In response to air or fluid pressure discharge through the ports 32 the pallet 35- oscillates on the shaft 36, as indicated by the dotted outline of the pallet arms and the curved arrowed line, in a short are to bring two stop plugs or detent elements 35A and 35B alternately into momentary engagement with the peripheral surface of the valve plate 30 at the inlet ports or openings 32 as they move successively past the pallet element and thus cause it to oscillate back and forth from one to the other.

With further reference to the construction as shown in FIG. 4, on the oscillatory pallet element 35 the stop plugs or detent elements 35A and 35B are positioned and spaced so that alternately the element 35A comes into engagement with the outlet port 32A to momentarily close it and restrain the valve plate 30 from rotational movement and then the stop element 35B comes into engagement with the outlet port 32B likewise to momentarily close it and restrain the valve plate 30 from rotational movement. In this alternating operating sequence, it will be seen that the air or gas pressure in the chamber 33 as applied through the inlet port 34A and the outlet port 32A to the stop element 35A, causes the latter to move to the left, as viewed in the drawing, from the position shown and opens the port 32A, thereby releasing the valve plate for rotational movement. This permits the outlet port 32B to move into place in front of the moving element 35B which then engages it.

At the same time inlet port 34B comes into registration with other arm 33B of the inlet chamber 33 and thus receives a pulse of gaseous or air pressure to dislodge the stop element 35B and cause the pallet to move again in the opposite direction, and again to the position as shown in FIG. 4. This step-by-step operation then continues as the valve plate or element 30 rotates under the power provided through the gearing and the rack 17 from the steadily moving piston element 7. While the piston thus mechanically drives the valve element 30 it also compresses the gas or air which provides the timing medium for release through the outlet ports 32 stepby-step in the manner above described.

As seen more clearly in FIG. 4, the pallet element 35 is operatively supported on the shaft 36 in front of and in tangential relation to the curved-outer or peripheral surface of the valve plate 30 and inertial control of the movement of the pallet 35 is provided by the two elongated pallet arms 38 which are of equal length and directly connected therewith.

At any time during operation of the system, the piston 7 may move back to the position shown without restraint from the stopping or step-by-step action of the detent elements 35A and 35B on the valve plate 30 because ratchet 27 provides slippage or ratchet-action as the block 18 and piston rod 15 move back with the piston. The gear train however, is relatively small and light and thereby imposes no appreciable load on the resetting action of the piston, particularly on launching since there is no air pressure to drive the pallet 35 and effect any detent action.

For operating the timing system under certain conditions, the cylinder 10 may be filled by compressed air or other gaseous medium from any suitable source. In the present example it may be considered to be filled from a compressed-air or gas tank 40, shown in dotted outline to indicate its alternative and infrequent use. The tank may have an output nozzle 41 for engaging the inlet opening 12 to apply the compressed gas or air to the cylinder. This operation serves to force the piston 7 back and thus to compress the return spring 8. The flow of compressed air or gas from the tank 40 may be con trolled by a suitable valve 42 provided with an operating button or handle 43.

This method of applying a charge to the cylinder, to move the piston 7 to the set position rearwardly, is utilized only in case the timing device is used in equipment which is not subject to setback on firing or launching. However, generally the piston 7 is moved backward to take in air through the opening 12 as the projectile or carrier moves in the direction of flight.

In this system the piston provides an inertial mass axially aligned with the direction of movement or the longitudinal flight axis of the space vehicle by which the timing system is carried, and is subject to a setback force on launching or firing of the vehicles into flight. This action fully compresses the return spring 8 and moves the piston 7 to the rear, or to the right as viewed in the drawing, from which posit-ion it moves after takeoff to drive the gearing and rotary valve element as previously described. Simultaneously, the gas or air charge in the cylinder 10 is leaked off at a fixed timing rate through the conduit 14 by the opening and closing action of the valve elements 35A and 35B of the pallet on the valve disk 30. Since the piston 7 moves under the driving action of the piston, pressure in the cylinder 10 and on the outlet ports remain substantially constant. This may further be maintained by means of temperature-sensitive material at the port openings which permit the outlet to slightly vary in size as the ambient temperature changes.

The operation of the system shown is such that upon launching or firing, the piston 7 moves in the direction of the arrow due to the force of setback and the valve 11 opens to admit air or other gas through the opening 12 to till the chamber or cylinder 10 from the open area of the projectile. Upon emergence from the launcher the projectile moves into flight with the setback forces removed, so that the valve 11 may close and the piston 7 may then move in the opposite direction. This applies force to the gear rack 17 which, in turn, moves the gear train and the linkage which rotates the valve element 30. Thus the cylinder with its inertial piston provides mechanical force and fluid pressure for the operation of the timing means. The compressed gas or air is metered or released in steps as the mechanism moves under control of the pallet in a step-by-step operation. This finally results in the exactly timed operation of the functional control element for the vehicle.

What is claimed is:

1. A self-powered timing system for space vehicles and the like, comprising in combination,

a closed air cylinder having an outlet conduit connected with the forward end thereof,

a piston movable in said cylinder and providing an inertial mass responsive to launching setback force to move rearwardly of said cylinder,

spring means connected with the piston to receive a compression force therefrom and drive said piston forward following setback,

means for deriving mechanical driving force and air pressure from said forward piston movement for timing control,

said last-named means including a piston rod connected with the piston to move therewith and a gear train connected to be driven by movement of said piston rod,

rotary valve means connected with said conduit and including a rotary timing pallet disk having a plurality of uniformly spaced radial outlet ports for releasing air from the cylinder through said conduit in response to forward movement of the piston,

means including a drive shaft for said timing disk connected with said gear train to provide a rotary driving force on said disk from said piston rod in response to forward movement of said piston,

an oscillatory pallet-type valve element positioned adjacent to the periphery of said timing disk to alternately cover each port in two successive rotational positions for metering the air outlet from said ports,

fixed valve means associated with the rotary timing pallet disk for connecting the outlet conduit with the covered port in each position,

thereby to control the rate of a flow from the cylinder and the piston forward movement, and

means positioned to be actuated for forward movement of the piston rod for effecting a timing control output from said system.

2. A self-powered timing system for space vehicles comprising in combination,

a movable piston element providing an inertial mass and having a piston rod movable therewith,

a cylinder element adapted for limited movement of said piston element therein from rest in a rearward direction in response to launching setback force applied thereto,

compression spring means connected for storing the inertial thrust of said piston element as a driving force therefor in a forward and opposite direction,

an outlet conduit connected with the cylinder forward of the piston range of movement to receive fluid pressure output therefrom in response to forward movement of the piston element,

a timing shaft driven by means responsive to forward moivement of said piston element through said piston r0 a function control element positioned to be actuated in response to movement of the piston rod to the forward end of its range of movement,

circular rotary outlet valve means driven by said timing shaft connected with the outlet end of said conduit to control the fluid outlet pressure from said cylinder and the rate of movement of the piston element against said presure,

said valve means having a plurality of uniformly angularly spaced peripheral outlet ports which move successively into communication with said conduit in response to rotation of said valve means, and

oscillatory pallet means positioned adjacent to the periphery of said valve means for engaging and closing said outlet ports in response to rotation of said valve means and repulsion therefrom by fluid outlet pressure successively in timed space relation.

3. A self-powered timing system for space vehicles as defined in claim 2,

wherein the said responsive means is driven by a gear train in connection with a gear rack carried by the piston rod, and

wherein the rotary valve means includes a rotary valve plate in the periphery of which the outlet ports are located and a fixed valve plate chambered to connect the outlet conduit with selected ones of said ports adjacent to the pallet means.

4. A self-powered timing system for space vehicles of the type subject to setback force in launching into flight, comprising in combination,

a closed fluid-pressure cylinder having charging inlet means connected with the forward end thereof,

a piston movable in said cylinder and providing an inertial mass responsive to launching setback force to move rearwardly of said cylinder,

spring means connected with the piston to receive a compression force therefrom and drive said piston forward following setback,

means for deriving both mechanical driving force and air pressure from said forward piston movement for timing control,

said last-named means including a piston rod connected with the piston to move therewith and a fluid pressure outlet conduit connected with the cylinder and communicating with the interior thereof forward of the piston range of movement,

rotary valve means connected with said conduit and including a rotary timing pallet disk having a plurality of uniformly spaced radial outlet ports for releasing fluid pressure from the cylinder through said conduit in response to forward movement of the piston,

means including a gear train connected to provide a rotary driving force on said timing disk from said piston rod in response to forward movement of said piston,

an oscillatory pallet-type valve element positioned adjacent to the periphery of said timing disk and pivotally movable to alternately cover each port in two successive rotational positions for metering the fluidpressure outlet from said ports,

fixed valve means associated with the rotary timing pallet disk for connecting .the outlet conduit with the covered port in each position,

thereby to control the rate of fluid flow from the cylinder and the piston forward movement, and

means positioned to be actuated by forward movement of the piston rod for effecting a timed function control output from said system.

5. A self-powered and self-regulated timing system for space vehicles of the projectile and rocket type comprising in combination,

a movable piston element providing an inertial mass,

a cylinder element adapted for movement of said piston element therein a forward composition of rest in a rearward direction through a predetermined range in response to setback force applied thereto in launching a carrier vehicle into flight,

compression spring means connected with said piston element for receiving the inertial thrust thereof for driving said element in the forward and opposite direction upon cessation of said force,

a piston rod connected and movable with said piston and extending externally of said cylinder,

an outlet conduit connected with the cylinder and communication with the interior thereof forward of the piston range of movement for receiving a fluidpressure outlet from said cylinder in response to forward movement of said piston element,

a timing shaft driven by means responsive to movement of said piston element and piston rod to be driven by the forward movement thereof,

a firing control element positioned to be actuated by the piston rod at the forward end of its range of movement,

circular rotary outlet valve means driven by said timing shaft connected with the outlet end of said conduit to release the fluid pressure in said cylinder forward of said piston element and to control the rate of movement thereof against said pressure,

said valve means having a plurality of uniformly angularly spaced outlet ports movable therewith successively into communication with said conduit in response to rotation thereof, and

oscillatory pallet means positioned adjacent to said valve means for alternately engaging and closing the 6 success1ve outlet ports in response to rotation of sald valve means and repulsion therefrom by said fluid pressure at said outlet conduit.

6. A self-powered and self-regulated timing system for space vehicles of the projectile and rocket type as defined in claim 5,

wherein the said responsive means is driven by a gear train in connection with a gear rack carried by the piston rod, and

wherein the rotary valve means includes a rotary valve plate in the periphery of which the outlet ports are located and a fixed valve plate chambered to connect the outlet conduit with selected ones of said ports adjacent to the pallet means.

7. A self-powered and self regulated timing system for vspace vehicles of the projectile and rocket types, comprising in combination,

a movable piston element providing an inertial mass and having a piston rod connected thereto and movable therewith,

a cylinder element adapted for limited movement of said piston element therein from rest in a rearward direction in response to launching setback force applied thereto,

compression spring means in the cylinder in rear of the piston element and connected therewith for storing the inertial thrust of said piston element and providing a driving force therefor in a forward and opposite direction,

a fluid outlet conduit connected with the cylinder forward of the piston range of movement to receive fluid pressure output therefrom in response to forward movement of the piston element,

a gear train and a gear rack meshing therewith connected to be driven through said piston rod in response to forward movement of said piston element,

a rotary timing shaft connected to be driven by said gear train,

a space-vehicle function control element positioned to be actuated by movement of the piston rod at the forward end of its range of travel,

rotary valve means including a fixed valve plate having a chamber connected with the outlet end of said conduit and a rotary valve plate connected to said timing shaft to control the fluid outlet pressure from said cylinder and the rate of movement of the piston element against said pressure,

said rotary valve plate being in face-to-face contact with said fixed valve plate and having a plurality of uniformly 'angularly spaced peripheral outlet ports which move successively into communication with said chamber in response to rotation of said valve means, and

oscillatory pallet means positioned adjacent to the periphery of said valve means and having stop plugs operative to engage and close said outlet ports successively in two positions in response to rotation of said valve means and repulsion therefrom in each of said two positions by fluid outlet pressure successively in timed spaced relation, thereby to provide timed movement of the piston rod and timed operation of said function control element.

References Cited UNITED STATES PATENTS 1,589,080 6/1926 Kyle 9135 3,262,374 7/1966 Trombatore et al. 9135 X 3,283,591 11/1966 Green 74-35 MILTON KAUFMAN, Primary Examiner. 

